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SERVICE TEST 



FLYING WING 

lorthrop 




MM 






BY AUTHORITY OF 
COMMANDING GENERAL 
AIR MATERIEL COMMAND 
U.S. AIR FORCE 



SIX J35-A- 19 

ALLISON 



14 OCT. 1949 



CONFIDENTIAL 



YRB-49A 



SERVICE TEST 



C 0-N-F4-0 E N-=^t-ftir 



-172.0 

5© 



J — L 



-44.2- 





Wing Area ... 
Aspect Ratio 



.4000 sq ft. 
.7.4 



Wing Section Root; NACA 65,3-019 
Tip; NACA 65,3-018 
M.A.C 315 in 



1239 gal(S.S.) 
1996 gal 
890 gal 
890 gal 
890 gal 
890 gal 
1996 gal 
1239 gal(S.S.) 




14.7 gal 
14.7 gal 
1068 gal 
14.7 gal 



1201gal(S.S. 
1321gal(S.S. 
1068 gal 
14.7 gal 
14.7 gal 
14.7 gal 



inwwwi Fuel 



I Oil 




YRB - 49A 



CONF IDENTiAL 



14 OCT. 1949 



SERVICE TEST 



G-O-N-F I O E ISFPt-ft-tr 



POWER PLANT 


No. & Model 


(6) J35-A-19 


Mfr 




Engine Spec. No. •• 


. Allison No. 280 


Type & Stages ... 


Axial (11) 




138.0" 




37.0" 


Weight (dry) 


2210 lb 



ENGINE RATINGS 


S.L. Static 


LB - RPM 


T.O: 


4900 - 7800 


Mil: 


4900 - 7800 


Nor: 


4240 - 7400 



dia 


IENSIONS 




172.0' 


Length .. 


53.1' 


Height .. 


20.1' 




44.2' 




The mission of the YRB-49A is to test the suitability of the flying 
wing configuration to photo-reconnaissance work. 

The crew consists of pilot, co-pilot -radio operator, radar -navigator, 
photo-navigator, and flight engineer plus provisions for a photo-tech- 
nieian. 

This aircraft is a modification of the B-35 (reciprocating engine) to 
accommodate six turbo-jet type engines and photographic equipment. 
The aircraft is of "pure" flying wing configuration using elevons (com- 
bination elevator & ailerons) and split type wing tip drag rudders for 
control. Four vertical fins are installed replacing four propellers and 
associated shaft housings. 

The crew compartment is pressurized to maintain an equivalent of 
5000 feet altitude up to 28,000 feet and a constant differential pressure 
above 28,000 feet. Emergency oxygen system is provided, as are win- 
dow defrosting, air conditioning, dust protection and sound proofing. The 
landing gear is of the tricycle type with steerable nose wheel. 



Construction completion 1st. airplane: 

January 1950 (estimated) 

First flight: February 1950 (estimated) 

First delivery: September 1950 (estimated) 



CAMERAS 



No. Type Lens Usage 

1 T-ll ..6" Mapping 

5 .... K-17 ..6",12",24".. 

1 K-22 ..6",12",24".. 

1 K-37 ..12". 

8 K-38 ..24",36" 

1 Q-15 Radar Record 



B 


O M B S 


No. 


Size Type 


6 .. 


188 lb ... T-89 Flash Bombs 


G 


U N S 


NONE 



WEIGHTS 

Loading Lb L. F. 

Empty 88.427(E) 

Basic 89.788(E) 

Design 206,000 2.0 

Combat .... *129,487 
MaxT.O. .. tl75,000 
Max.Land . J150,000 

(E) Estimated 
♦For basic mission 
t Limited by strength to 85% design 
gross weight pending static test. 
t Limited by strength. 



FUEL 

Location No. Tanks Gal. 

Wings outbd ... *2 2478 

Wings center ...2 3992 

Wings inbd 6 5696 

Wings inbd .... *2 2522 

♦Self -sealing Total 14,688 

Fuel Spec. AN-F-32.AN-F-48, 

AN-F-58 

Fuel Grade JP-1.100/130.JP-3 

OIL 

Capacity (gal) 88 

Spec AN-0-9 

Grade 1010 

ELECTRONICS 

VHF Command AN/ARC -3 

Liaison AN/ARC-8 

Combat Interphone 

Search Radar AN/APQ-24 

Navigational Radar .... AN/APN-9 



14 OCT. 1949 



q--q ^ p I D E N T I A L. 



YRB - 49A 



SERVICE TEST 



C ONDITIONS 



BASIC 



RADIUS 



BASIC 



RANGE 



OVERLOAD 



RADIUS 



FERRY 



RANGE 



TAKE-OFF WEIGHT (lb) 

Fuel & Oil (gal) 

Military Load (Flash Bombs) (lb) 

Total Ammunition (rds/cal) 

Wing Loading (lb/sq ft) 

Stall Speed (power off) (kn) 

TAKE-OFF DISTANCE SL ® 

Ground Run (no wind) (J) (ft) 

To Clear 50ft Obst ® (ft) 

CLIMB FROM SL 

Rate Of Climb at SL © (fpm) 

Time To 10,000 Feet © (min) 

Time To 20,000 Feet © (min) 

Service Ceiling (100 f.p.m.) © (ft) 

COMBAT RANGE © (n.mi) 

COMBAT RADIUS © (n.mi) 

Avg. Cruising Speed (kn) 

Total Mission Time (hr) 

Cruising Altitude (ft) 



I 

175,000 
12,280/88 
1128 
None 
43.75 
88 

4280 
5380 

1460 
7.95 
20.45 
29,200 

1110 
336 
6.8 

© 



M 

175,000 
18,280/88 
1128 
None 
43.75 
88 

4280 
5380 

1460 
7.95 
20.45 
29,200 
2250 

340 
6.7 

© 



III 

192,291 
14,688/88 
1128 
None 
48.00 
92 

5700 
7300 

1300 
9.28 
33.00 
27,000 

1155 

334 

6.9 



I V 

175,000 
12,450/88 
None 
None 
43.75 
88 

4280 
5380 

1460 
7.95 

20.45 
29,200 

2280 

340 
6.8 
® 



COMBAT WEIGHT 

Combat Altitude 
SPEED 

Max Speed (combat alt) 

Max Speed (Optimum alt.) Ft. 
CLIMB 

Rate Of Climb (combat alt) 

Rate Of Climb At SL 
CEILING 

Combat Ceiling (500 fpm) 

Service Ceiling (100 fpm) 

Service Ceiling (100 fpm) 
LANDING WEIGHT SL 

Ground Roll 

From 50' Obst. 



© 

© 
® 

© 



® 
® 



(lb) 
(ft) 

(kn) 
(kn) 

(fpm) 
(fpm) 

(ft) 
(ft) 
(ft) 
(lb) 
(ft) 
(ft) 



129,487 
35,000 

380 
381/35,332 

495 
2900 

34,500 
40,000 
37,300 
99,929 

1440 

3050 



99,929 
39,500 

381 
381/40,000 

600 
3940 

40,000 
45,500 
42,600 
99,929 

1440 

3050 



135,250 
32,000 

372 
381/35,800 

580 
2750 

33,500 
39,000 
36,250 
100,731 

1500 

3060 



129,572 
35,000 

380 
381/36,500 

495 
2900 

34,500 
40,000 
37,300 
100,043 

1445 

3050 



S N 



NOTES 




CONDITIONS: 


(T) Take-off power 


normal technique. For airport plan- 


(a) 


Performance Basis: Estimated data 


© Max power 


ning add 25% to distances shown. 


(b) 


In computing Radius and Range, specific fuel consumption has 


© Normal power 


© Detailed descriptions of the 




been increased 5% to allow for variations of fuel flow in service 


(D Take-off and landing distances 


RADIUS & RANGE missions are 




aircraft. 


are obtainable at sea level using 


given on page 6. 


(c) 


Performance is based on powers shown on page 3. 



YRB-49A 



CONFIDENTI AL 



14 OCT. 19 49 



SERVICE TEST 



&-OWIOEN-T-t-frt 




14 OCT. 1949 



CONFIDENTIAL 



YRB - 49A 



SERVICE TEST 



CONFIDENTIAL 



NOTES 

■ - ■ 

FORMULA: RADIUS MISSION I 



yn -v 



> \ %. Warm-up and take-off (allow 5 minutes normal power SL static fuel 



<S> » * flow) climb on course at maximum power to initial cruising altitude of 



o <s> 27,200feet. Cruise toward target at long range speeds utilizing a cruis- 

ing climb arriving at 33,500 feet 6 minutes prior to bomb drop. Con- 
duct 6 minute run into target at normal power, drop bombs, and conduct 
6 minute normal rated power evasive action (no distance). Using cruis- 
ing climb return to base at long range speeds arriving over base of 
40,000 feet. Landing and endurance reserve is 10% of initial fuel load. 



-TV 

i O 



* C 

3 



FORMULA: RANGE MISSION II 

Same as out bound leg of Mission I continued to point where 90% of 
fuel load has been consumed. Altitude at bomb drop is 39,500 feet. Land- 
ing and endurance reserve is 10% of initial fuel load. 



FORMULA: RADIUS MISSION m 



Same as Mission I except for increased fuel load and take-off weight. 
Initial cruise altitude is 24,000 feet, altitude over target is 32,000 feet, 
final altitude over base is 38,500 feet. Allowances are same as Mission 
I. 



FORMULA: RANGE MISSION IV 

Same as Mission n except for replacement of military load by fuel, 



YRB-49A 



CONFIDENTIAL 



14 OCT. 1949